Cathode ejector cooling flow control system

Abstract

An integrated hydrogen-electric includes a hydrogen fuel cell; a hydrogen fuel source; an electric motor assembly disposed in electrical communication with the fuel cell; n air compressor system configured to be driven by the motor assembly, and a cooling system having a heat exchanger radiator in a duct of the cooling system, and configured to direct an air stream including an air stream from the air compressor through the radiator, wherein an exhaust stream from a cathode side of the fuel cell is fed via an flow control nozzle into the air stream in the cooling duct downstream of the radiator.

What is claimed is: 
     
       1. A fuel cell powered airplane, comprising integrated hydrogen-electric engine including:
 a hydrogen fuel cell; 
 an air inlet coupled to a cooling duct integrated into the aircraft, and 
 a cooling system having a heat exchanger radiator in the cooling duct, and configured to direct an air stream comprising an air stream from the air inlet through the radiator, and wherein an exhaust stream from a cathode side of the fuel cell is fed into the cooling duct, wherein the cathode exhaust stream is fed via a flow control nozzle into the air stream in the cooling duct both upstream and downstream of the heat exchanger radiator, wherein the cathode exhaust feed into the air stream in the cooling duct downstream of the heat exchange radiator is introduced through a porous wall of the cooling duct. 
 
     
     
       2. The fuel cell powered aircraft of  claim 1 , wherein the duct includes a constricted section downstream of the flow control nozzle. 
     
     
       3. The fuel cell powered aircraft of  claim 1 , wherein the flow control nozzle is configured to inject the exhaust stream from the cathode side of the fuel cell tangentially to the air stream in the duct. 
     
     
       4. The fuel cell powered aircraft of  claim 1 , further comprising a valve configured to regulate mass flow or pressure of the cathode exhaust stream at the flow control nozzle. 
     
     
       5. The fuel cell powered aircraft of  claim 1 , further comprising a bypass outlet upstream of the flow control nozzle configured to maintain back pressure on the fuel cell. 
     
     
       6. A method for cooling a fuel cell aboard a fuel cell powered airplane, wherein the airplane includes an integrated hydrogen-electric engine including:
 a hydrogen fuel cell; 
 an air inlet coupled to a cooling duct integrated into the aircraft, and 
 a cooling system having a radiator in the cooling duct, the steps of: 
 directing an air stream from the air inlet through the radiator, and 
 feeding an exhaust stream from a cathode side of the fuel cell into the cooling duct, wherein the exhaust stream is fed via a flow control nozzle into the air stream in the cooling duct both upstream and downstream of the radiator, wherein the cathode exhaust feed into the airstream in the cooling duct downstream of the radiator is introduced through a porous wall of the cooling duct. 
 
     
     
       7. The method of  claim 6 , wherein the cooling duct includes a constricted section configured for decreasing pressure drop in air mass flow rate downstream of the cathode side exhaust stream feed. 
     
     
       8. The method of  claim 6 , wherein the exhaust stream from the cathode side of the fuel cell is fed tangentially to the air stream in the duct. 
     
     
       9. The method of  claim 6 , wherein a valve is provided upstream of the cathode side exhaust stream for regulating mass flow or pressure of the cathode exhaust stream at a flow control nozzle. 
     
     
       10. The method of  claim 6 , Wherein a bypass outlet is provided upstream of the cathode side exhaust stream feed to maintain back pressure on the fuel cell. 
     
     
       11. The method of  claim 6 , wherein a portion of the cathode side exhaust stream is mixed with bleed air from an air compressor system before being fed into the cooling duct. 
     
     
       12. The fuel cell powered aircraft of  claim 1 , wherein the cooling duct is integrated into wings and/or a fuselage of the aircraft. 
     
     
       13. The method of  claim 6 , wherein the cooling duct is integrated into wings and/or a fuselage of the aircraft.